The application and development of pulsed plasma thrusters (PPTs) in recent years are reviewed this paper. advantages PPTs discussed. schematics, propulsion performance parameters key physical processes described. Some representative PPT products flight systems developed presented to show the PPT. Studies about how electrode structures, discharge circuits, propellant materials, energy method, feed ignition method number thruster heads influence analyzed. ignitor design process carbonization...

Computational and theoretical models of millimeter-sized bubbles placed on upright hydrophobic superhydrophobic surfaces are compared with experimental data here. Although the for a surface corroborated computational data, case showed to be able contain significantly larger volumes than predicted. This is attributed greater ability bubble contact line advance its tendency detach from because buoyancy. We surmise that static model therefore describes only an unstable equilibrium these...

In the past several decades, use of electric propulsion in spacecraft has experienced tremendous growth. With increasing adoption small satellites kilogram range, suitable systems will be necessary near future. Pulsed plasma thrusters (PPTs) were first form to deployed orbit, and are highly for due their inherent simplicity. However, lifetime is limited by disadvantages such as carbon deposition leading thruster failure, complicated feeding required conventional solid propellants (usually...

An ablative pulsed plasma thruster (APPT) design with a 'segmented anode' is proposed in this paper. We aim to examine the effect that asymmetric electrode configuration (a normal cathode and segmented anode) has on performance of an APPT. The magnetic field discharge arc, density exit plume, impulse bit, thrust efficiency were studied using probe, Langmuir stand, mass bit measurements, respectively. When compared conventional symmetric parallel electrodes, anode APPT shows improvement up...

Pulsed plasma thrusters (PPTs) are a form of electric spacecraft propulsion. They have an extremely simple structure and highly suitable for nano/micro-spacecraft with weights in the kilogram range. Such small recently experienced increased growth but still lack efficient propulsion systems. PPTs operate pulsed mode (one discharge = one shot) typically use solid polytetrafluoroethylene (PTFE) as propellant. However, new non-volatile liquids perfluoropolyether (PFPE) family been found to be...

The transport of liquid droplets on surfaces carrying reactants offers advantages in the creation fluidic devices crucial for life science applications. In a majority situations, selection these surface, rather than all them, will need to be moved at any one time. It is formidable challenge deliver motive energy source only specific while leaving others unmoved. Here, we describe an alternative novel solution momentarily pinning surface allowing rest moved. We demonstrate this concept via...

Pulsed plasma thrusters are a form of electric propulsion for spacecraft. Their research has undergone recent growth due to an increasing interest in small satellites. However, their plumes transient and challenging study the extremely short discharge time that lasts order microseconds. The plume is accelerated by combination electrothermal electromagnetic forces. With acceleration, ions typically thought be only within thruster Lorentz force. Estimated downstream exhaust velocities have...

The ablative pulsed plasma thruster (APPT) has been widely used on satellites due to its low electrical power requirements and structural simplicity. Recently, a segmented anode schematic proposed increase the main discharge arc current density propellant mass ablation of APPTs while using same input energy. In this work, structurally similar multi-segmented was instead for measurements. incentive behind use measure propagation process downstream flow inside channel (volume between...

Discrete microfluidics offers distinct advantages over continuous since the need for flow presents significant problems. Here, we demonstrate a method of achieving gentle transfer liquid samples between two capillaries with use air actuation which limits and is amenable to automation. Since stability bridges in operation, there relationship established gap distance volume, thereby resulting three physical response types that were identified. Only one these allows efficient transfer. We...

Electric propulsion (EP) has become one of the most promising options for motion control small satellites. The physics behind ejected plasma plumes EP thrusters attracted significant interest due to their interactions with critical components Axisymmetric plume assumptions are widely used in simulations and diagnostics. However, we show here that a parallel-plate pulsed thruster (PPT) is asymmetrically distributed along centerline electrodes, contrary inherent axisymmetric assumption. To...

The ablative pulsed plasma thruster (APPT) is a typical form of electric propulsion that highly suitable for micro-satellites.However, its low performance has been main drawback.Recently, an asymmetric segmented anode schematic was shown to enhance the APPTs.The improved thrust obtained with use can potentially enable promising applications in future space tasks.To further understand physical processes behind APPT, experiments using ultra-high-speed camera, narrow bandpass filters, and...

Pulsed plasma thrusters (PPTs) have been widely used in space flight applications due to their low cost and robustness. Recently, it has observed that during the operation of a PPT, plume exhibits an in-plume acceleration phenomenon where leading-edge ions continue accelerate even absence electromagnetic forces. The physical mechanism behind may be ambipolar diffusion nature. However, details regarding propagation electrons within are still unknown. To better understand complete process, is...